# TCDS A60NM: Leonardo S.p.A. - Aircraft Division - Type: Type certificate data sheet - Status: Current - Holder: Leonardo S.p.A. - Aircraft Division - Revision: 1 - Revised: August 7, 2020 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Data sheet PDF: https://openairdocs.org/files/sha256/c3/9f/c39f4938b600921fc4198e1c85c3a22f90911ab91b0f3f3ee485fb087dfad14d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID160431261320231205170335.0001 - Page: https://openairdocs.org/tcds/A60NM ## Models (1) As the data sheet lists them. - C-27J JCA ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 Rev. No. 1 New New New 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A60NM Revision 1 Leonardo C-27J JCA August 7, 2020 FAA TYPE CERTIFICATE DATA SHEET NO. A60NM This data sheet which is part of Type Certificate No. A60NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Leonardo S.p.A. - Aircraft Division Piazza Monte Grappa, 4 00195 Rome, Italy Type Certificate Holder Record ALENIA AERONAUTICA S.p.A. Transferred TC No. A60NM to Leonardo S.p.A. on March 5, 2020 I. Model C-27J JCA (Transport Category Airplane) approved December 21, 2010 Engines Two (2) Allison / Rolls Royce AE2100D2A (Engine Type Certificate TE1CH, dated September 24, 2008) Fuel Fuels conforming to: ASTM D-1655 grades Jet-A and Jet A-1, MIL-T-5624 grade JP-5, and MIL-T-83133 grade JP-8 are acceptable. (see also the C-27J JCA Airplane Flight Manual AFM-1C-27J-JCA-1) Engine Limits Engine data sheet Power [SHP] Torque m × daN [ft × lb] MGT [°C] Np(*) [%] Ng(**) [%] Take-off (5 min.) 4637 234.9 (1732) 852 101 101 Maximum continuous 4637 234.9 (1732) 833 101 101 Transient - 262.1 (1933) - 114 102 (*) 100% = 14267 revolutions per minute [r.p.m.] (**) 100% = 15265 revolutions per minute [r.p.m.] Other engine limitations: See the Engine Type Certificate Data Sheet TE1CH Propeller Number and type: Two (2) - Dowty Propeller R391/6-132-F/10 Blades: Six (6) - composite material Diameter: 4115 mm (162 inches) Minimum propeller pitch angle in flight range: 15° (software), 13° (mechanical) Minimum propeller pitch angle in ground range: -17° Feathered propeller pitch angle: 89° Propeller Limits See the relevant Propeller Type Certificate Data Sheet P15BO A60NM 2 of 6 Auxiliary Power Unit Hamilton Sundstrand T-62T-46C16 APS 1000 Hydraulic Fluids Hydraulic Fluid specification:MIL-PRF-5606 or MIL-PRF-83282 Oil specification: MIL-L-23699 Engine and APU specification: MIL-L-7808 Airspeed Limits (I.A.S.) VMO 260 KIAS from sea level to 18,400 ft MMO 0.55 from 18,400 ft to 25,000 ft VA (Maneuvering) 199 KIAS from sea level to 25,000 ft at 67,241 lb (30,500 kg) VFE (Flaps Extended) 1 180 KIAS 2 170 KIAS FULL 155 KIAS VLE 200 KIAS VLO 155 KIAS Tire Speed 210 MPH Windshield wiper operating speed 203 KIAS Center of Gravity Limits Refer to the C-27J JCA Airplane Flight Manual (AFM-1C-27J-JCA-1) Datum Center line normal plane positioned 653 mm forward of the aircraft nose Leveling Means Mount points of airplane floor positioned at frame No. 20 on right side (10000 mm from datum) Maximum Weights Taxi and ramp: 30700 Kg (67681 lbs) Take-off: 30500 Kg (67240 lbs) Landing: 27500 Kg (60626 lbs) Zero fuel: 26500 Kg (58422 lbs) Minimum Crew Two (2): Pilot and copilot Number of Seats Three (3): Pilot, copilot and flight deck observer Maximum Compartment Weights Loading limitations referred to datum distances and measured in millimetres are: 5355 – 9145 1500 Kg/m and 600 Kg/m2 9145 – 10015 2500 Kg/m and 1000 Kg/m2 10015 – 11175 2500 Kg/m and 1000 Kg/m2 11175 – 12195 2500 Kg/m and 1000 Kg/m2 12195 – 13945 1500 Kg/m and 600 Kg/m2 13945 – 15905 1000 Kg/m and 400 Kg/m2 (ramp) Fuel Capacity Tanks Usable Fuel Unusable Fuel Liters (Kg) Gallons (lb) Liters (Kg) Gallons (lb) Wing Left Main Tank 3360 (2654) 888 (5852) 40 (32) 11 (70) Right Main Tank 3360 (2654) 888 (5852) 40 (32) 11 (70) Left Aux Tank 2800 (2212) 740 (4877) 57 (45) 15 (99) Right Aux Tank 2800 (2212) 740 (4877) 57 (45) 15 (99) Total 12320 (9732) 3256 (21458) 194 (154) 52 (338) NOTE: Weights are calculated for a typical JP-8 with an average standard day density of 790 kg/m3 Oil Capacity Engine oil: Two tanks with a capacity of 34 litres APU oil: One tank with a capacity of 4.73 litres Maximum Operating Altitude 25,000 ft (see Note 6) 3 of 6 A60NM Control Surface Movements Wing Flaps (outer/inner) 11.25°/5.0°, 22.5°/10.0° and 45.0°/20.0° Ailerons 26° up, 19° down (structural stop 27° up, 20° down) Spoilers 77.5° roll control 90° lift dumper (structural stop 91°) Elevator 25° up, 25° down (structural stop 27.5° up, 27.5° down Stabilizer fixed Rudder * 35° right, 35° left * NOTE: Rudder control system is equipped with a Rudder Travel Limiter Unit (RTLU) Serial Numbers No civil C-27J JCA customers are presently identified. Military configured C-27J JCA airplanes could be eligible for a U.S. civil standard certificate of airworthiness (See “Import Requirements”) if exported from Italy to the U.S. with an Export Certificate of Airworthiness that references the FAA approved civil type design with identified deviations; these deviations must be rectified before such airplanes will be eligible for a U.S. civil standard certificate of airworthiness. Import Requirements The FAA can issue a U.S. airworthiness certificate based on an Export Certificate of Airworthiness (Export C of A) signed by a representative of the ENAC on behalf of the European Community. The Export C of A should contain the following statement: ‘The a ircraft covered by this certificate has been examined, tested, and found to conform with the Type Design approved under U.S. Type Certificate No. A60NM and to be in a condition for safe operation.’ Certification Basis 14 CFR Part 25, effective February 1, 1965, including Amendments 25-1 through 25-87 in entirety, plus Amendment 25-111, effective September 2, 2003, for 14 CFR 25.856(a), Amendment 25-122, effective September 5, 2007, for 14 CFR 25.1317 and Amendment 25-125, effective September 19, 2008, for 14 CFR 25.981(b) and the fuel tank flammability requirements of 25.981(d), as described in exemption No. 9847, and to prevent a potential unsafe design feature under 14 CFR 21.21(b)(2), the applicant is required to comply with EASA Certification Specification CS 25.1155 at Amendment 5. Special Conditions No. 25-390-SC Interaction of Systems and Structures No. 25-391-SC Liquid Oxygen System No. 25-392-SC Unique Systems and Equipment within a Class E Cargo Compartment. NOTE: The FAA Special Conditions referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgSC.nsf/MainFrame?OpenFrameSet Equivalent Safety Findings 14 CFR 25.791(b): Lavatory Passenger Information Signs (documented in TAD ELOS memo TC0371IB-T-C-5); 14 CFR 25.1093(b): Air Intake System Ice Protection (documented in TAD ELOS memo TC0371IB-T-P-1); 14 CFR 25.1549: APU Instruments, Markings, and Placards (documented in TAD ELOS memo TC0371IB-T-P-2); 14 CFR 25.1305(e)(1): Engine Torque Indications (documented in TAD ELOS memo TC0371IB-T-P-3); 14 CFR Part 25 Subparts E, F, & G: Adoption of draft harmonized rules for Auxiliary Power Unit (APU) Certification (documented in TAD ELOS memo TC0371IB-T-P-10); 14 CFR 25.671(c)(2): Flight Control System Failure Criteria (documented in TAD ELOS memo TC0371IB-T-S-5); 14 CFR 25.831(g): Acceptable High Temperature Physiological Environment During Failure Conditions (documented in TAD ELOS memo TC0371IB-T-S-17). NOTE: The FAA Equivalent Level of Safety Memos referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgELOS.nsf/MainFrame?OpenFrameSet A60NM 4 of 6 Exemptions Exemption No. 9737 for 14 CFR Part 25 Section 25.562(b)(2), Amendment 25-64, “Emergency landing dynamic conditions”; Exemption No. 9847 for 14 CFR Part 26 Section 26.37 (b), Amendment 26-2, “Pending type certification projects: Fuel tank flammability”. NOTE: The FAA Exemptions referenced above may be accessed at internet location: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgEX.nsf/MainFrame?OpenFrameSet Optional Requirements complied with: §25.1403 Wing icing detection lights; §25.1419 Ice protection. Continued Airworthiness and Safety Improvements Special Federal Aviation Regulation (SFAR) Number 88, Amendment 21-78, became effective June 6, 2001. SFAR No. 88, “Fuel Tank System Fault Tolerance Evaluation Requirements”, is applicable to the C-27J JCA. Alenia Aeronautica must satisfy the requirements of SFAR No. 88 within 18 months after issuance of the type certificate. 14 CFR Part 26, effective September 19, 2008, including Amendment 26-2. Environmental Standards 14 CFR P art 36, effective December 1, 1969, including Amendments 36 -1 through 36-28; 14 CFR P art 34, effective September 10, 1990, including Amendments 34 -1 through 34-3. Additional Design Requirements and Conditions The following design details or information must be maintained to ensure that an unsafe design condition is not present: Severe Icing Conditions: Airplanes with pneumatic deicing boots and non-powered lateral axis flight controls can be more susceptible to a potential loss of control following an exposure to supercooled large drop icing conditions. Specific visual cues for identifying severe icing conditions for the C -27J were determined, and the airplane was shown to be controllable after such an encounter and capable of safely exiting these conditions. The Airplane Flight Manual (AFM) Limitations (Section 2-5 “Systems” and Section 2-7 “Icing Conditions”), Normal Procedures (Section 3-17 “Flight Conditions”) and Emergency Procedures (Section 4A -12 “Miscellaneous”) contain instructions for identifying severe icing conditions and procedures for safely exiting such conditions. Reverse Thrust and Propeller Pitch Settings below the Flight Regime: The C-27J includes a feature named “Beta Lock -Out System” to protect the intentional activation of the Reverse Thrust and Propeller Pitch Settings below the Flight Regime in flight. This Beta Lock-Out System is compliant with the requirements of EASA CS 25.1155 at Amendment 5. The Airplane Flight Manual (AFM) Limitations (Section 2-4 “Power Plant”), Emergency Procedures (Section 4A -2 “ACAWS” and Section 4A -3 “Engine”) and Procedures F ollowing Failures (Section 4B-2 “ACAWS” and Section 4B-20 “Avionics System”) contain instructions for operation during beta lock-out system malfunctions. Class E Cargo Compartment - Protection of essential systems: Cargo Compartment Lining panels are installed in the cargo compartment in order to assure protection against flame penetration for all essential systems and equipment. These panels meet the flame penetration resistance requirements of Appendix F Part III of JAR-25 (Change 14 Amendment 25/96/1). The Cargo Compartment Lining consists of: • sidewall panels installed from frame 9 to frame 29; • ceiling panels installed from frame 9 to frame 32. Following a smoke event, the flight crew will apply the relevant Airplane Flight Manual (AFM) Emergency Procedures to shut -off cargo ventilation, depressurize the cabin to 5 of 6 A60NM 24,000 feet and start emergency descent and landing as soon as possible (Section 4A -5 “Smoke”). Fuel Tank Vent System Flame Arrestors: The fuel vent outlets of the Model C-27J include flame arrestors to prevent fuel tank explosions following an accident. Flame arrestors must be maintained that have flame holding capability for a minimum period of 2.5 minutes to allow passenger evacuation following an accident. The flame arrestor installation must also be designed such that either ice will not accumulate during icing conditions or the fuel tank pressures will be maintained within allowable limits by other means when the arrestor installation ices over. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see the Certification Basis) must be installed in the aircraft. As referenced in the paragraph 2.2 of Doc. ref. G-CONF-110/090-0100-0002-AL Issue 14 “C-27J – Civil Certification – Type Design Definition”, the lists of all equipment as well as optional approved equipment are contained in the document: Doc. ref. G-CONF-110/090-0100-0016-AL Issue 1 “Equipment Qualification List”. Airplane Flight Manual EASA approved C-27J JCA Airplane Flight Manual AFM-1C-27J-JCA-1 Service Information Each of the documents listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by Alenia Aeronautica under the authority of EASA Design Organization Approval EASA.21J.003 are considered FAA approved. These approvals pertain to the design data only. • Alenia Aeronautica Service Bulletins, except as noted below, • Structural repair manuals • Vendor manuals referenced in Alenia Aeronautica Service Bulletins • Airplane flight manuals • Repair instructions. Note: Design changes that are contained in Alenia Aeronautica Service Bulletins and that are classified as Level 1 Major or non-basic in accordance with either the US/Italy or US/EASA Bilateral Aviation Safety Agreement - Implementation Procedures for Airworthiness, must be approved by the FAA. NOTES NOTE 1. A current weight and balance report, including a list of equipment included in the certificated empty weight, and loading instructions when necessary must be provided for each aircraft at the time of original certification. For further information see Weight and Balance Manual WBM-1C-27J-JCA-5. NOTE 2. Airworthiness Limitations including structural inspections and retirement times for safe-life parts are listed in Doc. ref. G-CONF-110/090-0100-0017-AL Issue 1. NOTE 3. Certification Maintenance Requirements are listed in Doc. ref. G-CONF-110/090-0100-0017-AL Issue 1 Section 4. NOTE 4. Instructions for continued airworthiness (ICA) are incomplete. ICA must be complete and accepted by the FAA prior to delivery of the first airplane or issuance of a standard certificate of airworthiness, whichever occurs later. Contact the TC issuing office, AIR-731, for information. NOTE 5. Other Operating Limitations: - The FAA pilot type rating has not been determined. No U.S. C -27J JCA pilot certificates may be issued until this is accomplished. - Operational suitability under 14 CFR Parts 91, 125, and 121 has not been evaluated. This aircraft may not be operated under those regulations until this evaluation has been accomplished. A60NM 6 of 6 NOTE 6. FAA ACOs should coordinate with the TC issuing office (AIR-731) any changes intended to increase the airplane maximum operating altitude above 25,000 feet (reference Issue Paper G-1). ...END... ``` ## ADs None name its models. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.